CN109850159A - One kind is based on the recoverable unmanned plane during flying winterization system of heat - Google Patents
One kind is based on the recoverable unmanned plane during flying winterization system of heat Download PDFInfo
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- CN109850159A CN109850159A CN201910122577.2A CN201910122577A CN109850159A CN 109850159 A CN109850159 A CN 109850159A CN 201910122577 A CN201910122577 A CN 201910122577A CN 109850159 A CN109850159 A CN 109850159A
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- heat
- defroster
- heat dissipation
- unmanned plane
- working medium
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Abstract
The invention discloses one kind based on the recoverable unmanned plane during flying winterization system of heat, belongs to air vehicle technique field.The unmanned plane during flying winterization system includes heat-energy recovering apparatus, heat dissipation defroster, working medium circulation pipeline；The heat-energy recovering apparatus is set to the aero-engine radiator portion of unmanned plane front end, the heat dissipation defroster includes the first heat dissipation defroster, the second heat dissipation defroster, the first heat dissipation defroster is respectively arranged on the wing of the unmanned plane two sides, the second heat dissipation defroster is set on the empennage of the unmanned plane rear end, and the heat-energy recovering apparatus, the first heat dissipation defroster, the second heat dissipation defroster by the working medium circulation piping connection and are formed into a loop.The present invention solves the technical issues of existing hot gas deicing system and electrothermal deicing system exacerbation unmanned vehicle engine load.
Description
Technical field
It is especially a kind of based on the recoverable unmanned plane during flying winterization system of heat the invention belongs to air vehicle technique field.
Background technique
The complicated multiplicity of the application environment of unmanned plane, various factors influence the flying quality and state of unmanned plane.Unmanned plane exists
When high-altitude flight, it is easy to freeze because of low temperature with due to encountering steam, especially the windward sides such as the leading edge of a wing, empennage leading edge, head.Nothing
After man-machine icing, increase body weight, so as to cause the gravity center instability of fuselage, nobody flight and movement are generated can not be pre-
The influence seen, even results in aircraft accident；The aerodynamic configuration of aircraft is destroyed simultaneously, increases resistance, reduces lift, it is also possible to can lead
Cause distorted signals or retardance, it is therefore desirable to which a kind of antifreeze deicer ensures the safety of flight.At present frequently with hot gas remove
Ice system and electrothermal deicing system need engine or power supply directly to provide energy, this will increase the load of engine, reduces nothing
Man-machine lifting capacity and influence airframe structure.
Summary of the invention
Goal of the invention of the invention is to provide one kind based on the recoverable unmanned plane during flying winterization system of heat, which is used for
The technical issues of solving existing hot gas deicing system and electrothermal deicing system exacerbation unmanned vehicle engine load.
In order to achieve the above objectives, the technical scheme adopted by the invention is that:
One kind is based on the recoverable unmanned plane during flying winterization system of heat, including heat-energy recovering apparatus, heat dissipation defroster, work
Matter circulation line；
The heat-energy recovering apparatus is set at the aero-engine radiator portion of unmanned plane, and the heat dissipation defroster includes
First heat dissipation defroster, the second heat dissipation defroster, the first heat dissipation defroster are set at left and right sides of the unmanned plane
On the inside of the windward side of wing, the second heat dissipation defroster is set on the inside of the windward side of unmanned plane rear end empennage；
The heat-energy recovering apparatus includes Dissipated heat recovery device and waste gas recovering device, and the Dissipated heat recovery device is wrapped in
The wind-cooling heat dissipating piece position on aero-engine top, the heat distributed for recycling wind-cooling heat dissipating piece, the waste gas recovering device
Set on the exhaust position of aero-engine, for recycling the exhaust gas of unmanned vehicle engine generation, the heat-energy recovering apparatus difference
It is connected to by working medium circulation pipeline with the first heat dissipation defroster and the second heat dissipation defroster, the work of the waste gas recovering device
Matter entrance passes through working medium circulation pipeline respectively and is connected to the first heat dissipation defroster and the second heat dissipation defroster, and the exhaust gas returns
The sender property outlet of receiving apparatus is connected to the Dissipated heat recovery device；
When unmanned plane starting, the heat that the Dissipated heat recovery device distributes wind-cooling heat dissipating piece is recycled, described useless
The exhaust gas that gas recovering device generates unmanned vehicle engine recycles, and heat is driven successively to transmit by Dissipated heat recovery device
One heat dissipation defroster and the second heat dissipation defroster, return the working medium entrances of waste gas recovering device, finally by exhaust gas later
The sender property outlet of recyclable device is passed back to Dissipated heat recovery device again and completes a cycle.
Further, the Dissipated heat recovery device include insulated heat set, heat-resisting heat conductive silica gel, heat conducting pipe, tightening sleeve and
Zipper；
The insulated heat set is wrapped in the wind-cooling heat dissipating piece position on aero-engine top, and the insulated heat set is two
Layer Oxford cloth clamp felt, the heat-resisting heat conductive silica gel are set in insulated heat set, and the heat-resisting heat conductive silica gel is dissipated with air-cooled
Backing outer surface is conformal, is filled with phenol formaldehyde foam between the heat-resisting heat conductive silica gel and insulated heat set；The heat conducting pipe is set to
Between the insulated heat set and heat-resisting heat conductive silica gel, the heat conducting pipe is the multiple ring pipe for being surrounded on wind-cooling heat dissipating piece periphery
Road, the heat conducting pipe outside cover inside and heat-resisting heat conductive silica gel adhesion, the zipper and tightening sleeve with insulated heat respectively and are set to
Insulated heat is put on.
Further, the waste gas recovering device includes exhaust-gas treatment room and working medium process chamber, and the exhaust-gas treatment room is set
In the rear of working medium process chamber；
It is communicated with gas sampling pipe on the left of the exhaust-gas treatment room, for collecting the exhaust gas of unmanned vehicle engine generation,
It is communicated with exhaust pipe on rear side of the exhaust-gas treatment room, for exhaust gas to be discharged, the gas sampling pipe and exhaust pipe pass through connecting tube
Connection, the connecting tube are equipped with by-passing valve；
The front side of the working medium process chamber is equipped with working medium entrances, and the right side of the working medium process chamber is equipped with sender property outlet；
Position opposite the first impeller and the second leaf are vertically arranged in the exhaust-gas treatment room and working medium process chamber respectively
Wheel, is equipped with shaft between first impeller and the second impeller, first impeller and the second impeller are respectively arranged in described turn
The both ends of axis；
When unmanned plane starting, the working medium entrances collect the heat of the Dissipated heat recovery device recycling, and the exhaust gas is received
The exhaust gas that collector generates unmanned vehicle engine recycles, and exhaust gas enters exhaust-gas treatment room and drives the first wheel rotation, it
Exhaust gas is discharged through exhaust pipe again afterwards, and first impeller drives the second wheel rotation, the power that the second impeller generates by heat by
Dissipated heat recovery device is transferred to the first heat dissipation defroster and the second heat dissipation defroster, is finally passed back to heat dissipation recycling dress again
It sets；By adjusting the by-passing valve, the flow of exhaust gas can be controlled, the revolving speed of the first impeller is adjusted.
Further, the first heat dissipation defroster includes heat-dissipating pipe, cooling fin and bracket, the cooling fin and heat dissipation
Pipe by bracket is installed on wing inner cavity, and the arc-shaped shape in the top of the cooling fin, lower part is tapered plane, the cooling fin it is upper
Portion is fitted closely with airfoil inner surface, and lower part is fixed by the bracket, and the bracket is made by rigid polyurethane foam；It is described
The structure of second heat dissipation defroster is identical as the first heat dissipation structure of defroster.
Further, the preceding stationary point face of the front end of the heat-dissipating pipe and wing, the rear end of the heat-dissipating pipe passes through bracket
It is fixed on the wing inner cavity.
Further, the working medium circulation pipeline is phenolic aldehyde insulation tube.
Due to the adoption of the above technical scheme, the invention has the following advantages:
1. the Dissipated heat recovery device in the present invention can recycle the heat that unmanned vehicle engine wind-cooling heat dissipating piece distributes, exhaust gas
Recyclable device can recycle exhaust gas, and using its thermal energy and kinetic energy as the power source of working medium circulation pipeline, make Dissipated heat recovery device
The heat of recycling is conducted to the first heat dissipation defroster and the second heat dissipation defroster, then passes Dissipated heat recovery device back, so as to
Enough play the role of carrying out antifreeze deicing to the wing and empennage of unmanned plane；The present invention passes through recycling unmanned vehicle engine itself
Thermal energy, reaches effect identical with electro-thermal deicing, energy conservation and environmental protection and lighter than the weight of similar product, and it is whole to improve unmanned plane
The performance of body increases unmanned plane lifting capacity.
2. waste gas recovering device of the invention can utilize the first wheel rotation of exhaust gas driven, and drive the rotation of the second impeller
As the power source of working medium circulation pipeline, be conducive to adequately utilize the thermal energy and kinetic energy of exhaust gas.
3. the working medium circulation pipeline in the present invention is filled using phenol formaldehyde foam, be conducive to reduce heat during heat transmitting
The loss of amount.
Detailed description of the invention
Fig. 1 is the principle of the present invention figure；
Fig. 2 is the structural schematic diagram of Dissipated heat recovery device of the present invention；
Fig. 3 is the structural schematic diagram of the waste gas recovering device in the present invention；
Fig. 4 is the structural schematic diagram of the first heat dissipation defroster in the present invention.
Main element symbol description is as follows in figure:
In attached drawing, 1- waste gas recovering device, 2- Dissipated heat recovery device, the heat dissipation of 3- first defroster, the heat dissipation of 4- second are anti-
Freeze device, 5- working medium circulation pipeline, 7- insulated heat set, 8- heat conducting pipe, the heat-resisting heat conductive silica gel of 9-, 10- tightening sleeve, 11- zipper,
12- gas sampling pipe, 13- exhaust pipe, 14- working medium entrances, 15- sender property outlet, 16- by-passing valve, 17- wing, 18- cooling fin,
19- heat-dissipating pipe, 20- bracket, at 21- icing critical, 22- wind-cooling heat dissipating piece.
Specific embodiment
It is further illustrated below in conjunction with specific implementation of the attached drawing to invention.
As shown in Figure 1, a kind of based on the recoverable unmanned plane during flying winterization system of heat, including heat-energy recovering apparatus, heat dissipation
Defroster, working medium circulation pipeline 5；Heat-energy recovering apparatus is set at the aero-engine radiator portion of unmanned plane, is radiated antifreeze
Device includes the first heat dissipation heat dissipation defroster 4 of defroster 3, second, and the first heat dissipation defroster 3 is set to unmanned plane or so two
On the inside of the windward side of side wing 17, the second heat dissipation defroster 4 is set on the inside of the windward side on the empennage of unmanned plane rear end；Thermal energy returns
Receiving apparatus includes Dissipated heat recovery device 2 and waste gas recovering device 1, and Dissipated heat recovery device 2 is wrapped in the wind on aero-engine top
Cold 22 position of cooling fin, the heat that the wind-cooling heat dissipating piece 22 for recycling unmanned vehicle engine distributes, waste gas recovering device 1 are set to
The exhaust position of aero-engine, for recycling the exhaust gas of unmanned vehicle engine generation.Heat-energy recovering apparatus passes through working medium respectively
Circulation line 5 is connected to the first heat dissipation defroster 3 and the second heat dissipation defroster 4, the working medium entrances 14 of waste gas recovering device 1
It is connected to respectively by working medium circulation pipeline 5 with the first heat dissipation defroster 3 and the second heat dissipation defroster 4, waste gas recovering device 1
Sender property outlet 15 be connected to Dissipated heat recovery device 2；When unmanned plane starting, Dissipated heat recovery device 2 dissipates wind-cooling heat dissipating piece 22
The heat of hair is recycled, and the exhaust gas that waste gas recovering device 1 generates unmanned vehicle engine recycles, and passes through moving exhaust gas
Heat can be driven successively to transmit the first heat dissipation defroster 3 and the second heat dissipation by Dissipated heat recovery device 2 with thermal energy as power source
Defroster 4 returns the working medium entrances 14 of waste gas recovering device 1 later, finally by the sender property outlet 15 of waste gas recovering device 1
It is passed back to Dissipated heat recovery device 2 again and completes a cycle.
As shown in Fig. 2, Dissipated heat recovery device 2 includes that insulated heat covers 7, heat-resisting heat conductive silica gel 9, heat conducting pipe 8, tightening sleeve 10
With zipper 11；Insulated heat set 7 is wrapped in 22 position of wind-cooling heat dissipating piece on aero-engine top, and insulated heat set 7 is two layers
Oxford cloth clamp felt.Heat-resisting heat conductive silica gel 9 and heat conducting pipe 8 are set in insulated heat set 7, and heat conducting pipe 8 is located at heat-proof silica gel 9 and exhausted
Between Thermal protection set 7, heat conducting pipe 8 be the multiple ring-like pipeline for being surrounded on the periphery of wind-cooling heat dissipating piece 22, on the outside of heat conducting pipe 8 with it is heat-resisting
9 close adhesion of heat conductive silica gel and heat-resisting heat conductive silica gel 9 and 22 outer surface of wind-cooling heat dissipating piece are conformal, logical convenient for heat-resisting heat conductive silica gel 9
It crosses the temperature difference heat transfer that solid is contacted with solid and absorbs the heat that the wind-cooling heat dissipating piece 22 of engine distributes, then pass through solid
The working medium in heat conducting pipe 8 is transmitted to liquid thermal convection；The outside of heat conducting pipe 8 and heat-insulating protective layer adhesion, secure heat conducting pipe 8 and its
Connected heat-resisting heat conductive silica gel 9.It is steeped in addition to remaining place of heat conducting pipe 8 with phenolic aldehyde between heat-resisting heat conductive silica gel 9 and insulated heat set 7
Foam filling, reduces heat loss.Zipper 11 on insulated heat set 7 is received for the ease of mounting and dismounting heat-energy recovering apparatus
Fixed 10 are set to the two sides of insulated heat set 7, and tightening sleeve 10 prevents from falling off for locking fastening.
As shown in figure 3, waste gas recovering device 1 includes exhaust-gas treatment room and working medium process chamber, exhaust-gas treatment room is set to working medium
The rear of process chamber；Gas sampling pipe 12 is communicated on the left of exhaust-gas treatment room, for collecting the useless of unmanned vehicle engine generation
Gas, exhaust-gas treatment room rear side are communicated with exhaust pipe 13, and for exhaust gas to be discharged, gas sampling pipe 12 and exhaust pipe 13 pass through connecting tube
Connection, connecting tube are equipped with by-passing valve 16；The front side of working medium process chamber is equipped with working medium entrances 14, and the right side of working medium process chamber is equipped with
Sender property outlet 15；Position opposite the first impeller and the second leaf are vertically arranged in exhaust-gas treatment room and working medium process chamber respectively
Wheel, is equipped with shaft between the first impeller and the second impeller, the first impeller and the second impeller are respectively arranged in the both ends of shaft；Work as nothing
When man-machine starting, working medium entrances collect the heat that Dissipated heat recovery device 2 recycles, and gas sampling pipe 12 generates unmanned vehicle engine
Exhaust gas recycled, exhaust gas enter exhaust-gas treatment room and drive the first wheel rotation, exhaust gas is discharged through exhaust pipe 13 again later,
First impeller drives the second wheel rotation, and heat is transferred to first by Dissipated heat recovery device 2 and dissipated by the power that the second impeller generates
Hot defroster 3 and the second heat dissipation defroster 4, are finally passed back to Dissipated heat recovery device 2 again；By adjusting by-passing valve 16, energy
The flow for enough controlling exhaust gas, adjusts the revolving speed of the first impeller.
As shown in figure 4, the first heat dissipation defroster 3 is respectively arranged on the inside of the windward side of unmanned plane two sides wing 17, second
The defroster 4 that radiates is set on the inside of the windward side of unmanned plane rear end empennage.First heat dissipation defroster 3 and the second antifreeze dress of heat dissipation
It is identical to set 4 structural principles, only size is different, is all to return by working medium circulation pipeline 5 from the heat dissipation of heat-energy recovering apparatus
Receiving apparatus 2 obtains thermal energy and waste gas recovering device 1 and obtains kinetic energy, and it is antifreeze to exchange heat with the external world, after again working medium circulation pipeline 5 return
Thermal energy is reacquired to Dissipated heat recovery device 2 and waste gas recovering device 1 reacquires kinetic energy, is recycled as one.With first
It radiates for defroster 3, similarly, the first heat dissipation defroster 3 includes heat-dissipating pipe 19, cooling fin to the second heat dissipation defroster 4
18 and bracket 20, cooling fin 18 and heat-dissipating pipe 19 are installed on wing 17 by bracket 20.17 front end of wing is at icing critical
Surface before 21 is easy icing area, and heat dissipation defroster is mainly in 17 inner cavity of wing of this part.Heat-dissipating pipe 19 is from heat
The Temperature of Working highest just flowed out in energy recyclable device, antifreeze ability is most strong, so staying before 19 front end face wing 17 of heat-dissipating pipe
Point is aerofoil temperature lowest part, and 19 rear end of heat-dissipating pipe is supported by the curved surfaces of 20 front end of bracket and fixes.Cooling fin 18 is top
Arc is fitted closely with 17 inner surface of wing, and lower part is that tapered plane is supported by bracket 20.Because the working medium in cooling fin 18 is
Through radiating by heat-dissipating pipe 19 so heat has had lost a part, but its after-heat can still make full use of, so making
For cooling fin 18, it is antifreeze that heat is provided to the less low region of temperature in easy icing area, and being sufficiently will be remaining in working medium
Heat utilization, so its section is flat.Bracket 20 is made by rigid polyurethane foam, is on the one hand cooling fin 18 and heat dissipation
Pipe 19 provides support, on the other hand, heat is locked in 17 front end inner cavity of wing as heat-insulating material, reduces thermal loss.Work
Matter circulation line 5 is phenolic aldehyde insulation tube.
Above description is the detailed description for the present invention preferably possible embodiments, but embodiment is not limited to this hair
Bright patent claim, it is all the present invention suggested by technical spirit under completed same changes or modifications change, should all belong to
In the covered the scope of the patents of the present invention.
Claims (6)
1. one kind is based on the recoverable unmanned plane during flying winterization system of heat, which is characterized in that anti-including heat-energy recovering apparatus, heat dissipation
Freeze device, working medium circulation pipeline；
The heat-energy recovering apparatus is set at the aero-engine radiator portion of unmanned plane, and the heat dissipation defroster includes first
Radiate defroster, the second heat dissipation defroster, and the first heat dissipation defroster is set to wing at left and right sides of the unmanned plane
Windward side on the inside of, it is described second heat dissipation defroster be set to unmanned plane rear end empennage windward side on the inside of；
The heat-energy recovering apparatus includes Dissipated heat recovery device and waste gas recovering device, and the Dissipated heat recovery device is wrapped in aviation
The wind-cooling heat dissipating piece position of upper position of engine, the heat distributed for recycling wind-cooling heat dissipating piece, the waste gas recovering device are set to
The exhaust position of aero-engine, for recycling the exhaust gas of unmanned vehicle engine generation, the heat-energy recovering apparatus passes through respectively
Working medium circulation pipeline is connected to the first heat dissipation defroster and the second heat dissipation defroster, and the working medium of the waste gas recovering device enters
Mouth is connected to by working medium circulation pipeline with the first heat dissipation defroster and the second heat dissipation defroster respectively, the waste gas recovery dress
The sender property outlet set is connected to the Dissipated heat recovery device；
When unmanned plane starting, the heat that the Dissipated heat recovery device distributes wind-cooling heat dissipating piece is recycled, and the exhaust gas returns
The exhaust gas that receiving apparatus generates unmanned vehicle engine recycles, and drives heat successively to transmit first by Dissipated heat recovery device and dissipate
Hot defroster and the second heat dissipation defroster, return the working medium entrances of waste gas recovering device, finally by waste gas recovery later
The sender property outlet of device is passed back to Dissipated heat recovery device again and completes a cycle.
2. as described in claim 1 a kind of based on the recoverable unmanned plane during flying winterization system of heat, which is characterized in that described to dissipate
Heat recovery apparatus includes insulated heat set, heat-resisting heat conductive silica gel, heat conducting pipe, tightening sleeve and zipper；
The insulated heat set is wrapped in the wind-cooling heat dissipating piece position on aero-engine top, and the insulated heat set is two layers N
Saliva cloth clamp felt；The heat-resisting heat conductive silica gel is set in insulated heat set, the heat-resisting heat conductive silica gel and wind-cooling heat dissipating piece
Outer surface is conformal, is filled with phenol formaldehyde foam between the heat-resisting heat conductive silica gel and insulated heat set；The heat conducting pipe is set to described
Between insulated heat set and heat-resisting heat conductive silica gel, the heat conducting pipe is the multiple ring-like pipeline for being surrounded on wind-cooling heat dissipating piece periphery,
Cover inside and heat-resisting heat conductive silica gel adhesion on the outside of the heat conducting pipe with insulated heat respectively, the zipper and tightening sleeve are set to insulation
On protective case.
3. as claimed in claim 2 a kind of based on the recoverable unmanned plane during flying winterization system of heat, which is characterized in that described useless
Gas recovering device includes exhaust-gas treatment room and working medium process chamber, and the exhaust-gas treatment room is set to the rear of working medium process chamber；
It is communicated with gas sampling pipe on the left of the exhaust-gas treatment room, it is described for collecting the exhaust gas of unmanned vehicle engine generation
It is communicated with exhaust pipe on rear side of exhaust-gas treatment room, for exhaust gas to be discharged, the gas sampling pipe is connected to exhaust pipe by connecting tube,
The connecting tube is equipped with by-passing valve；
The front side of the working medium process chamber is equipped with working medium entrances, and the right side of the working medium process chamber is equipped with sender property outlet；
Position opposite the first impeller and the second impeller, institute are vertically arranged in the exhaust-gas treatment room and working medium process chamber respectively
It states and is equipped with shaft between the first impeller and the second impeller, first impeller and the second impeller are respectively arranged in the two of the shaft
End；
When unmanned plane starting, the working medium entrances collect the heat of the Dissipated heat recovery device recycling, the gas sampling pipe
The exhaust gas generated to unmanned vehicle engine recycles, and using the kinetic energy of exhaust gas and thermal energy as the first impeller of power source drive
Rotation, exhaust gas is discharged through exhaust pipe again later, and first impeller drives the second wheel rotation, and the power that the second impeller generates will
Heat is transferred to the first heat dissipation defroster and the second heat dissipation defroster by Dissipated heat recovery device, is finally passed back to and radiates back again
Receiving apparatus；By adjusting the by-passing valve, the flow of exhaust gas can be controlled, the revolving speed of the first impeller is adjusted.
4. as described in claim 1 a kind of based on the recoverable unmanned plane during flying winterization system of heat, which is characterized in that described the
One heat dissipation defroster includes heat-dissipating pipe, cooling fin and bracket, and the cooling fin and heat-dissipating pipe are installed in wing by bracket
Chamber, the arc-shaped shape in the top of the cooling fin, lower part is tapered plane, and the top of the cooling fin is closely pasted with airfoil inner surface
It closes, lower part is fixed by the bracket, and the bracket is made by rigid polyurethane foam；The knot of the second heat dissipation defroster
Structure is identical as the first heat dissipation structure of defroster.
5. as claimed in claim 4 a kind of based on the recoverable unmanned plane during flying winterization system of heat, which is characterized in that described to dissipate
The front end of heat pipe and the preceding stationary point face of wing, the rear end of the heat-dissipating pipe is fixed by the bracket in the wing inner cavity.
6. as described in claim 1 a kind of based on the recoverable unmanned plane during flying winterization system of heat, which is characterized in that the work
Matter circulation line is phenolic aldehyde insulation tube.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910122577.2A CN109850159A (en) | 2019-02-18 | 2019-02-18 | One kind is based on the recoverable unmanned plane during flying winterization system of heat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910122577.2A CN109850159A (en) | 2019-02-18 | 2019-02-18 | One kind is based on the recoverable unmanned plane during flying winterization system of heat |
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| Publication Number | Publication Date |
|---|---|
| CN109850159A true CN109850159A (en) | 2019-06-07 |
Family
ID=66898188
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910122577.2A Pending CN109850159A (en) | 2019-02-18 | 2019-02-18 | One kind is based on the recoverable unmanned plane during flying winterization system of heat |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112550733A (en) * | 2020-12-22 | 2021-03-26 | 中国航空发动机研究院 | Thermal management system for aircraft |
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| CN206035676U (en) * | 2016-08-31 | 2017-03-22 | 昆山市易泰汽车科技有限公司 | Engine waste gas double - circuit recirculation system |
| CN107218112A (en) * | 2017-07-25 | 2017-09-29 | 江西清华泰豪三波电机有限公司 | The radiator and engine system of engine exhaust driving |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112550733A (en) * | 2020-12-22 | 2021-03-26 | 中国航空发动机研究院 | Thermal management system for aircraft |
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